Design method of aeroengine intake total pressure distortion generating device
An aero-engine and generating device technology, which is applied in the direction of engine testing, jet engine testing, gas turbine engine testing, etc., can solve problems such as design and manufacturing difficulties, and achieve the effects of saving manufacturing costs and shortening the test cycle
Active Publication Date: 2021-08-03
XIAMEN UNIV
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Problems solved by technology
In practical engineering applications, the plate-shaped total pressure distortion generating device is widely used, but its design and manufacture are a major difficulty. If it is necessary to obtain a relatively fine and accurate total pressure distortion flow field, the distortion generating plate needs to be able to The position of the flow field produces an expected obstruction, which poses a challenge to the design and processing of the distortion generating plate
At the same time, if it is necessary to carry out a large number of tests on the total pressure distortion characteristics of the engine, the replaceability of the test piece is also very important. The design, processing and manufacture of the test piece need to consider the cost of manpower and material resources
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[0036] In order to make the technical problems, technical solutions and beneficial effects to be solved by the present invention clearer and clearer, the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments.
[0037] figure 1 Shown is a schematic diagram of the aero-engine intake total pressure distortion test bench, (1) is the test bench support, the tested aero-engine (2) and the air inlet (3) are installed on the thrust guide rail (4), and the thrust guide rail ( 4) Installed on the test bench support (1), during the test process of the aero-engine, the aero-engine (2) and the inlet (3) together with the thrust guide rail (4) can move back and forth in a small range along the axis of the engine, (5) It is the flow direction of the air sucked into the aero-engine during the test.
[0038] figure 2 Shown is the schematic diagram of aero-engine (2) and air inlet (3), the basic structure of the air inlet (3...
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The invention relates to a design method of an aeroengine intake total pressure distortion generating device, which belongs to the field of aeroengine test system design. This design method is based on the principle of air intake grille, and proposes to use deformable materials, take the airfoil grille as the basis of deformation, and use the air pump to inflate or pump air into the distortion generating device to increase or decrease the windward area of the airfoil grille , and considering the overall clogging degree of the grille, a reusable aero-engine intake total pressure distortion generation device with individually controllable spatial distribution of the steady-state circumferential total pressure distortion and the steady-state radial total pressure distortion is finally designed. The application of the design method can save the manufacturing cost of the steady-state total pressure distortion generating device of the aeroengine, and shorten the test cycle of the total pressure distortion of the aeroengine.
Description
technical field [0001] The invention belongs to the design field of aero-engine test systems, and in particular relates to a design method of an aero-engine intake total pressure distortion generating device. Background technique [0002] The function of the air intake of the aircraft is to capture the flow and quality airflow required by the aeroengine and transport it to the engine inlet to meet the needs of the engine's stable operation. In a real flight environment, the outlet of the air inlet, that is, the airflow at the inlet of the aeroengine will inevitably have uneven temporal and spatial distribution of airflow parameters such as velocity, pressure, and temperature. It is called aeroengine intake distortion. The distortion of the total pressure of the airflow at the inlet of an aeroengine will affect the stable working range of the engine and directly affect the performance of the aircraft propulsion system. Engine total pressure distortion index is an important ...
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IPC IPC(8): G01M15/14G01M15/02
CPCG01M15/02G01M15/14
Inventor 徐文江滕健
Owner XIAMEN UNIV